Aircraft

ABSTRACT

An aircraft having a fuselage of generally saucerlike character comprising upper and lower disc components separated by a transverse spacing; said upper component being contoured to provide an aerodynamic surface and merging into an upwardly projecting dome which comprises a portion of the pilot compartment. The maximum diameter of said upper component being substantially equivalent to three times the linear distance between the lower face of said spacing and the uppermost point of said dome. Depending from the lower fuselage section is a motor with a swivelly mounted afterburner for controlling the direction of horizontal flight. Provided within said spacing for rotation about an axis normal to the vertical axis of said aircraft are jet motors and airfoils for controlling vertical flight.

' UnitedStats Patent Inventor JohnW Thomley 3050 N. Brett Ave., Decatur,Ill. 62526 [21] Appl. No. 849,685 [22] Filed Aug. 13, 1969 [45] PatentedAug. 17, 1971 [54] AIRCRAFT 2 Clnlms, 7 Drawlng Flgs. I

52 U.S.C| 244/12, 244/43, 244/ l 23 [51] Int.Cl. 1364c 29/00 [50] FieldolSearch.... 244/12, 23, 123, 43; 60/261 [56] References Cited UNITEDSTATES PATENTS 2,713,393 7/1955 Isacco 244/43 2,743,072 4/1956 Emmi..244/43 3,065,938 11/1962 Calkins.... 244/43 3,497,163 2/l970 Wakefield244/43 Vi 4,l1 9 15%.? 2. 112

Primary Examiner-Milton Buchler Asristant Examiner-Steven W. WeinriebAttorney-Ralph W. Kalish ABSTRACT: An aircraft having a fuselage ofgenerally saucerlike character comprising upper and lower disccomponents separated by a transverse spacing; said upper component beingcontoured to provide an aerodynamic surface and merging into an upwardlyprojecting dome which comprises a portion of the pilot compartment. Themaximum diameter of said upper component being substantially equivalentto three times the linear distance between the lower face of saidspacing and the uppermost point of said dome. Depending from the lowerfuselage section is a motor with a swivelly mounted afterburner forcontrolling the direction of horizontal flight. Provided within saidspacing for rotation about an axis normal to the vertical axis of saidaircraft are jet motors and airfoils for controlling vertical flight.

PATENTEDAUBI 11971 3.599.902

SHEET 1 OF 3 5 F|G.l /2 l /2 l v I /z 2 INVENTOR ATTORNEYPATENTEDAUBHIQII 3.5991902 SHEEI 2 [IF 3 FIG. 6

INVENTOR JOHN W. THOMLEY BY QM- Kw ATTORNEY PATENTED AUG] 7197:

SHEET 3 0F 3 INVENTOR JOHN W. THOMLEY BY QM w-QM ATTORNEY .FIGURE 1. v 1

AIRCRAFT BACKGROUND AND SUMMARY OF THE INVENTION This invention relatesin general to aircraft and, more particularly, to a jet-propelledaircraft of general saucerlike design adapted for both horizontal andvertical flight. It is an object of the present invention to provideaircraft of the jet propulsion type incorporating a compact, so-calledsaucerlike fuselage and having retractable airfoils for takeoff andvertical flight purposes.

' It is a further object of the present invention to provide an aircraftof the type stated incorporating a fuselage having critical dimensionalcharacteristics for conducing to a level of operating efficiencyheretofore unknown in aircraft of generally related contour. It is afurther object of the present invention to provide an aircraft of thetype stated incorporating a fuselage having an upper portion with apredetermined camber to produce unusual lift characteristics, whereby alowpressure area or vacuum is created over substantially the entireupper surface of the craft with resultant lift ability to an extenthitherto unknown.

It is another object of the present invention to provide an aircraft ofthe type stated involving novel and easily manipulated means fordirecting the craft in horizontal flight.

It is a still further object of the present invention to provide anaircraft of the jet propulsion type which may be most economicallymanufactured; which is extremely efficient and low cost in operation;which, by reason'of its unique structure, is stable in flight; and whichis reliable and durable in usage.

DESCRIPTION OF THE DRAWINGS FIG. 1 is a front view of an aircraftconstructed in accordance with and embodying the present invention, withthe wings extended and with the aircraft supported upon its landinggear.

FIG. 2 is a side elevational iew taken on the line 2-2 of FIG. 3 is aside view illustrating the aircraft in flying condition. FIG. 4 isa'horizontal section taken on the line 4-4 of FIG.

FIG. 5 is a fragmentary view taken on the line 5-5 of FIG. 1,illustrating the afterburner of the drive jet in various positions. FIG.6 is a horizontal sectiontaken on the line 6-6 of FIG.

FIG. 7 is a horizontal section taken on the line 7-7 of FIG. 3. a

DESCRIPTION OF THE PREFERRED EMBODIMENT Referring now by referencecharacters to the drawings which illustrate the preferred embodiment ofthe present invention, A generally designates an aircraft having afuselage 1 of relatively shallow, so-called saucerlike configurationcomprising upper and lower, generally disc-shaped portions or shells 2,3, respectively, having, respectively, lower and upper confronting,coextensive, transversely extending, annular walls 4, 5 in spaced-apart.relationship to define therebetween a spacing 6 of shallow, cylindricalform, and being open throughout its peripheral -extent for purposespresently appearing. Said upper and lower fuselage portions 2, 3 arejoined by a column 7 presented centrally of spacing 6 and suitablysecured to said upper and lower portions 2, 3 for integrating theaircraft fuselage.

The exterior surface. of fuselage upper portion 2 is contoured todevelop a camber, as indicated at 8, for providing said portion withunusual aerodynamic characteristics. Upper fuselage portion 2 mergesinto a central dome 9 which constitutes the-exposedportion of a pilot'scompartment 10; said dome being designed to permit maximum streamliningfor reducing resistance to the relative and' true winds. Lower fuselageportion 3 is relatively shallow having a slightly concave lower surfaceas in the order of one-half to five degrees but with the side of saidportion being formed on a substantially same curve as the adjacent,lower section of upper fuselage portion 2. Said lower fuselage 3 in itslower end surface contains, preferably, three sets of swingably mounteddoors or panels, as indicated at 11,11 for accommodating a retractablelanding gear 12. It is to be observed that said sets of doors 11,11 aredisposed so as to present the landing gear members 12 in conventionaltricycle relationship so that the wheels of one landing gear, as at 12,willbe presented normally forwardly of, and aligned with a pointintermediate, the remaining two landing gear members 12,12. Said landinggear 12 are thus capable of being withdrawn into the interior offuselage lower portion 3 with the associated doors 11,11" being closedso as to conduce to streamlining during'flight (see FIG. 3), all as iswell known with current aircraft.

The diameter of upper fuselage portion 2 immediately adjacent spacing 6,or in other words, its maximum di'a"rrie ter,"is of such extent as to besubstantially equal to three times the distance between the upper faceof transverse wall Sand the apex or pinnacle of dome 9, as indicatedat13,'and measured along a line coaxial with column 7. Experiments havedemonstrated that such dimensional relationship conduces tom'aximumefiiciency in operation of aircraft A so that the said relationship, or3-to-1 ratio, is critical for optimum performance" Mounted upon column 7for rotative movement thereabout, by means to be described, is a bearing14 which may be of the conventional friction-reducing type, such as aroller or ball bearing, comprehending inner and outer races (not shown)with such bearing being supplied with a suitable lubricant, all as iswell known in the art. Bearing 14 constitutes the hub of a rotor,generally indicated 15, which comprises a pair of oppositely extendingdiametrically aligned sleeves 16, 16' being rigid at their inner endswith bearing 14 and receiving through their outer open ends support arms17, 17' which extend beyond the margins of spacing 6 for carrying ontheir outer end extremities a rocket or jet-type motor 18, 18' withtheir burners or exhaust ends directed oppositely so that upon firingthe thrust developed will create a torque for effecting rotation ofrotor 15. Fuel is supplied to each motor 18, 18 through lines (notshown) extending from a reservoir or tank (not shown) located withinaircraft A, preferably in lower fuselage portion 3; said lines extendthrough column 7, sleeves 16,16, and arms 17,17 in a manner currentlyaccepted. Sleeves 16,16 are adapted for rotative movement about theirlongitudinal axes that the related motors 18, 18 may be adjustablebetween horizontal and vertical attitude. Control means for presentingmotors 18,18 are manipulatable from remote mechanisms within the pilotscompartment 10. Although the drawings would indicate that the maximumcross section of motors 18, 18 is greater than the height of spacing 6so that seemingly retraction of said motors 18,18 thereinto would not beattainable, it is to be understood that appropriate alteration in suchdimensional relationships is within the scope of the present inventionso that' such motors 18,18 could be adapted for retractioii Such featu eis particularly important when aircraft A is to be used above the earthsatmosphere since in such environment, said' motors, as well as wings 21,21', will be of no purpose for vehicle propulsion.

Also be reason of the swingability of motors 18,18 the same maybe'utilized to continue to provide lift for aircraft A for overcomingany gravitational pull as within the upper reaches of the atmosphere.

Also integrally formed with hub 14 and extending in opposite directionstherefrom along an axis normal to that developed by sleeves 16,16 arecylinders 19,19 of fluid character and each having a piston 20,20,respectively, for

parent that wings 21, 21' are of appropriate thickness so as to bereceived between confronting walls 4,5 of spacing 6, inwardly of theouter margin thereof when the related pistons 20,20 are retracted (asshown in phantom lines in FIG. 4). Each wing 21,21 incorporates a pairof telescopic sections 22, 23 and 22, 23', respectively, being ofunderstandably relatively decreasing transverse extent; and which arecoaxial with the related wing 21,21, serving to increase the aerodynamicsurface thereof when fully extended (as shown in full lines in FIG. 4).By means known in the art, pistons 20,20 are adapted for limitedrotation about their major axis so that the related wings 21,21 may betilted for altering the angle of attack thereof. It is, of course,recognized that suitable pump mans and fluid reservoir are provided atan appropriate point within fuselage 1 for connection to cylinders 19,19for effecting retraction and extension of pistons 20,20 as required.

Depending from the central portion of the lower end surface of lowerfuselage portion 3 is a hollow mounting 24 for a single jet motor 25,the longitudinal axis of which is aligned with landing gear 12' forextension fore and aft of said aircraft A. At its rearward end, jetmotor or rocket 25, surrounding its discharge passage 26, is contouredto form a ball 27 for swivelly mounting thereon in the nature of a balland socket joint formation, an afterburner 28 having an interior,rearward tapering compartment 29 terminating in an outlet 30 fordischarge therethrough, at the expected high velocity, of the burningrocket contents. Such discharge, in accordance with accepted practice,causes a forward thrust to be imparted to the aircraft A therebyconstituting reaction propulsion. However, by reason of the swivelmounting of afterburner 28, the direction of discharge through outlet 30may be altered in a substantial range so that the reaction force will bein a correspondingly opposite direction thereby serving to control thedirection of movement of aircraft A in horizontal flight. Means foroperating afterburner 28 for commensurately moving same to effect travelalong the desired course, is provided within aircraft A for facilemanipulation by the pilot.

ln view of the foregoing, it will thus be seen that aircraft A isuniquely adapted for both vertical and horizontal flight and provingefficient movement through the atmosphere by reason of the uniqueaerodynamic characteristics developed by the contouring of aircraft A.

Thus, with aircraft A supported u'pon landing gear 12 combustion of fuelwithin jet motors 18,18 is initiated so that thrust is developed upondischarge to thereby cause hub 14 with its related structure to rotateabout the axis developed by column 7. It is understood that wings 21,21will have been placed in extended position so as to be caused to move ina circular path about fuselage l and with such movement creating an areaof negative pressure above said wings to impart lift of aircraft A. Uponupward travel of aircraft A the camber of fuselage 1 will conduct toextension of the negative pressure area above the fuselage upper portion2 and compartment so that maximum lift is developed. After aircraft Ahas reached a desired altitude, wings 21,21 may be withdrawn intospacing 6 for removal from path of travel of aircraft A in which suchcombustion of fuel within jet motor 25 will provide the propulsive forcefor the horizontal travel of aircraft A. As stated above, suchhorizontal flight is directionally controlled by appropriate operationof afterburner 28 which is quite easily achieved.

It should be understood, however, that landing gear 12 may be optionallyused since aircraft A may rise vertically from the ground without theneed of any runway and may also be maneuvered for landing withoutextension of the landing gear. The same are accordingly provided foroperation at the election of the pilot.

in view of the foregoing, it is to be seen that the pilot, throughrequisite control of jet motors 18,18 may effect corresponding controlof wings 21,21 so as to have a most fine range of adjustments suitablefor takeoff, flight and landing.

Having thus described my invention, what I claim and hope to obtain byLetters Patent is: x I

1. An aircraft comprising a fuselage having a discrete upper portion anda discrete lower portion, said upper and lower portions havingspaced-apart, parallel, confronting walls to define an interveningspace; said spacing being open to the atmosphere throughout itsperipheral extent; a column provided centrally of said spacingconnecting said upper and lower fuselage portions; bearing meansprovided surroundingly of said column in the region of said spacing; apair of diametrically opposed fluid cylinders connected to and extendingradially outwardly of said bearing means; a piston received within eachcylinder; means for effecting extension and retraction of said piston;airfoil lift-producing means operatively connected to the cylinderremote end of each piston; said piston having a length so that uponextension of said airfoil lifting means are positioned outwardly of theperipheral spacing opening beyond said fuselage, and upon retraction,are received inwardly of the peripheral spacing opening between saidfuselage upper and lower confronting walls; a pair of diametricallyopposed sleeves connected to and extending radially outwardly of saidbearing means in circumferentially spaced relationship with said fluidcylinders; a support arm received within each sleeve; means foreffecting extension and retraction of said support arm'within saidsleeve; propulsion means mounted on the sleeve remote end of saidsupport arms for effecting rotation of said airfoil lift-producingmeans; each of said support arms having a length so that upon extensionsaid propulsion means are positioned outwardly of the peripheral openingof said spacing beyond said fuselage and, upon retraction, are receivedwithin said spacing between said fuselage confronting walls.

2. An aircraft as defined in claim 1, and further characterized by saidconfronting walls of said upper and lower fuselage portions having adiameter substantially three times the distance between the wall of saidlower fuselage portion and the uppermost point of said upper fuselageportion.

1. An aircraft comprising a fuselage having a discrete upper portion anda discrete lower portion, said upper and lower portions havingspaced-apart, parallel, confronting walls to define an interveningspace; said spacing being open to the atmosphere throughout itsperipheral extent; a column provided centrally of said spacingconnecting said upper and lower fuselage portions; bearing meansprovided surroundingly of said column in the region of said spacing; apair of diametrically opposed fluid cylinders connected to and extendingradially outwardly of said bearing means; a piston received within eachcylinder; means for effecting extension and retraction of said piston;airfoil lift-producing means operatively connected to the cylinderremote end of each piston; said piston having a length so that uponextension of said airfoil lifting means are positioned outwardly of theperipheral spacing opening beyond said fuselage, and upon retraction,are received inwardly of the peripheral spacing opening between saidfuselage upper and lower confronting walls; a pair of diametricallyopposed sleeves connected to and extending radially outwardly of saidbearing means in circumferentially spaced relationship with said fluidcylinders; a support arm received within each sleeve; means foreffecting extension and retraction of said support arm within saidsleeve; propulsion means mounted on the sleeve remote end of saidsupport arms for effecting rotation of said airfoil liftproducing means;each of said support arms having a length so that upon extension saidpropulsion means are positioned outwardly of the peripheral opening ofsaid spacing beyond said fuselage and, upon retraction, are receivedwithin said spacing between said fuselage confronting walls.
 2. Anaircraft as defined in claim 1, and further characterized by saidconfronting walls of said upper and lower fuselage portions having adiameter substantially three times the distance between the wall of saidlower fuselage portion and the uppermost point of said upper fuselageportion.